Fluid turbomotor

ABSTRACT

A fluid turbomotor comprising a radial turbine wheel of the radial inflow type, a single stage axial turbine wheel on the same shaft as the radial wheel, and a blade type nozzle structure interposed between the radial and axial wheels, wherein the working fluid is introduced at the radial periphery of the radial wheel, is discharged at an axial face of the radial wheel into the nozzle structure, and is directed by the blades of the nozzle structure into the axial turbine wheel; also disclosed is a novel nozzle ring structure for the radial turbine wheel comprising two side-by-side blade sets of different angular orientation which are selectively moved into working relationship to the inflow of the radial wheel to vary the direction at which the working fluid is delivered to the radial wheel. The invention turbomotor is disclosed as the power source in an overhead cable hoist structure.

United States Patent [1 1 Chute [451 July 31, 1973 FLUID TURBOMOTORRichard Chute, Huntington Woods, Mich.

[73] Assignee: Eaton Corporation, Cleveland, Ohio [22] Filed: Sept. 22,1970 [21] Appl. No.: 74,463

[75] Inventor:

4/1951 France 415/158 1/1929 Great Britain 415/150 [57] ABSTRACT A fluidturbomotor comprising a radial turbine wheel of the radial inflow type,a single stage axial turbine wheel on the same shaft as the radialwheel, and a blade type nozzle structure interposed between the radialand axial wheels, wherein the working fluid is introduced at the radialperiphery of the radial wheel, is discharged at an axial face of theradial wheel into the nozzle structure, and is directed by the blades ofthe nozzle structure into the axial turbine wheel; also disclosed is anovel nozzle ring structure for the radial turbine wheel comprising twoside-by-side blade sets of different angular orientation which areselectively moved into working relationship to the inflow of the radialwheel to vary the direction at which the working fluid is delivered tothe radial wheel. The invention turbomotor is disclosed as the powersource in an overhead cable hoist structure.

6 Claims, 14 Drawing Figures PATENIEDJUL31 ms ,749,513

sum 1 or 5 I: l INVENTOR 5' 2515/54/4 6%Z/7c E- I L w/w PATENTED 1749.513

saw u [If 6 BACKGROUND OF INVENTION This invention relates toimprovements in fluid turbomotors. Various forms of turbomotors havebeen proposed and/or made commercially available. While theseturbomotors, considered in each case with respect to their intendedpurpose, have been generally satisfactory, none has offered thecombination of a relatively high stall torque ratio and reasonablyefficient operation in a reverse mode. Furthermore, none of the priorart turbomotors has offered a completely satisfactory mechanism formodulating the working fluid inflow to the turbomotor. Also, none of theprior art turbomotors is capable of satisfying all of the unique powerand controllability requirements of a cable type hoist.

SUMMARY OF THE INVENTION It is an object of the present invention toprovide an improved fluid turbomotor.

A more specific object is to provide a fluid turbomotor having arelatively high stall torque ratio coupled with an ability to operatewith reasonable efficiency in a reverse mode.

Another specific object is to provide an improved fluid modulatingmechanism for controlling the delivery' of the working fluid to a radialturbine wheel.

Another specific object is to provide a turbomotor which is uniquelysuited for use as the power source of a cable type hoist.

According to an important feature of the invention, the turbomotorcomprises a radial turbine wheel and an axial turbine wheel coupled to acommon shaft with a first nozzle assembly surrounding the radially outerperiphery of the radial wheel and a second nozzle assembly interposedbetween the turbines; the working fluid is directed by the first nozzleassembly into the radial periphery of the radial wheel, is discharged atan axial face of the radial wheel into the second nozzle assembly, andis directed by the second nozzle assembly into the blades of the axialturbine. In the disclosed embodiment, the second nozzle assembly is ofthe blade type and the blades of the axial turbine wheel are positionedat an angle such that, at the rated speed of the turbometer, thevectorial sum of the relative fluid leaving velocity of the blades ofthe axial turbine and the blade tangential velocity of the axial turbineblades is substantially equal to the vector of the fluid leaving theblades of the second nozzle assembly. With this vectorial relationship,at rated speed of the turbomotor, the axial turbine will windmill andthe radial wheel will supply substantially all of the torque output ofthe motor.

According to another important feature of the invention, the nozzleassembly for the radial turbine wheel comprises two side-by-side bladesets with different blade angles, and the turbomotor includes means forshifting the nozzle assembly between a first position in which one ofthe blade sets is aligned with the outer periphery of the turbine wheeland the other blade set is displaced with respect to the wheelperiphery, and a second position in which the other blade set is alignedwith the outer periphery of the wheel and the first blade set isdisplaced with respect to the wheel periphery. In the disclosedembodiments, the one blade set is arranged to rotate the turbine wheelin one direction and the other blade set is arranged to rotate the wheelin the reverse direction.

Other objects and features of the invention will be apparent from thedetailed description of the preferred embodiments and from theaccompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS In the drawings:

FIG. 1 is a perspective view of a cable hoist mechanism embodying aturbomotor according to the invention;

FIG. 2 is an end view of the hoist mechanism of FIG. I looking in thedirection of the arrow 2 in FIG. 1;

FIG. 3 is a longitudinal, fragmentary cross-sectional view taken on line3-3 of FIG. 2;

FIG. 4 is an enlarged view of the nozzle structure seen in circle 4 ofFIG. 3;

FIGS. 5 and 6 are similar to FIG. 4 but showing moved positions of thenozzle structure;

FIG. 7 is a cross-sectional view taken on line 77 of FIG. 4;

FIGS. 8, 9 and 10 are respective isolated end views, looking in thedirection of the arrows 8, 9 and 10 of FIG. 3, of a radial turbinewheel, axial turbine wheel, and axial turbine nozzle assembly embodiedin the invention turbomotor;

FIG. 11 is a fragmentary cross-sectional view taken on line 1lll of FIG.3;

FIG. 12 is a stall torque ratio graph for the invention turbomotor;

FIG. 13 illustrates a modified form of nozzle structure; and

FIG. 14 is a cross-sectional view taken on line l4-l4 of FIG. 13.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT The inventionturbomotor is disclosed as the power source for a cable type hoist. Thehoist seen in FIG. 1

includes a drum 10, a cable 12 wrapped in helical fashion around drum10, a load hook 13 carried in reeved fashion by cable 12, a pair oftracks 14 for supporting the drum, a carriage l6 rollably guiding ontracks 14 and including a journal portion 17 rotatably supporting thedrum, and a nut structure 18 including a partial ball nut 20 guiding ina vacant portion of the helical drum groove to thread the drumleftwardly or rightwardly along the track structure in response toclockwise or counterclockwise rotation of the drum so that the payout orpay-in location of cable 12 remains fixed as the cable is unwound fromor wound on the drum. Details of the construction and operation of thehoist of FIG. 1 are shown and described in copending U.S. Pat.application Ser. No. 76,514 filed on Sept. 29, 1970 and assigned to theassignee of the present invention.

A turbomotor seen generally at 22 in FIG. 1 is positioned within thehollow end of drum [0 and is arranged to selectively drive the drum inforward and reverse directions to pay-in or pay-out the cable.Turbomotor 22 is seen in end view in FIG. 2 and in longitudinal crosssection in FIG. 3, to which reference is now made.

Turbomotor 22 includes a housing seen generally at 24. Housing 24 is athree-part structure including an end housing 26, a central housing 28,and a brake housing 30. A central output shaft 32 is journalled inhousings 26 and 28; end 320 of shaft 32 is joumalled in double ballbearings 34, 36 positioned in a sleeve 38 received in the central hubportion 26a of end housing 26. An oil seal 40 is also received in sleeve38 and sealingly engages shaft end 32a. The other shaft end 32b isjournalled in a ball bearing 41 positioned in a sleeve 42. Sleeve 42 isreceived in the hub portion 44a of a wheel member 44 rigidly positionedin bell-mouth portion 28a of central housing 28. Wheel member 44includes an outer annulus or rim portion 44b interconnected to hubportion 44a by spokes 440; a set screw 46 carried by housing portion 28aengages rim portion 44b to rigidly position wheel member 44 within theturbomotor housing.

A radial turbine wheel 48 is keyed to shaft 32 adjacent shaft end 32a.Radial wheel 48 is of the radial inflow type. As seen in FIGS. 3, 8 and11, wheel 48 includes a central hub portion 50, an end wall portion 52at the right-hand axial face of the wheel as viewed in FIG. 3, and aplurality of vanes or blades 54 formed integrally with portions 50 and52. Each vane 54 includes a radial inflow portion 540 extending from theradially outer periphery of the wheel inwardly at an angle generallytangent to the outer periphery of hub portion 50, and an axial dischargeportion 54b which is bent over with respect to radial inflow portion 54aand defines, in cooperation with an adjacent discharge portion 54b, anaxial discharge passage for discharge of the working fluid at theleft-hand axial face of wheel 48 as viewed in FIG. 3.

Fluid leaving radial wheel 48 enters an axial turbine wheel nozzlestructure seen generally at 56. Nozzle structure 56, as best seen inFIGS. 3, l and 11, includes an annulus portion 56a secured in neckportion 28b of housing 28 by set screw 58, and a plurality of inwardlydirected blades 56b spaced circumferentially about the lengthwise axisof shaft 32 but defining a central opening for passage of the pilot endof radial wheel hub portion 50. Blades 5617 may number, for example,between 15 and 20 and may, for example, be inclined, as seen in FIG. 10,at an angle of approximately with respect to a radius of annulus 56a.

Working fluid is directed by nozzle assembly 56 into an axial turbinewheel seen generally at 60. Axial turbine wheel 60, as best seen inFIGS. 3, 9, and 11, includes a hub portion 60a keyed to shaft 32 and. aplurality of blades or vanes 60b radiating outwardly from hub portion60a. Blades 60b may number, for example, between l5 and 20 and may, forexample, be inclined, as seen in FIG. 9, at an angle of approximatelywith respect to a radius of hub 60a. The rightward pilot end (FIG. 3) ofhub portion 600 is secured to the left-hand pilot end of hub portion 50by a plurality of pins 62. A spacer 64 is positioned on shaft 32 betweenthe inner race of bearing 41 and the left face of hub portion 60a and anut 66 coacts with threads on shaft end 32b to snug ball bearing 41,spacer 64, hub 60a, hub 50, and ball bearings 34, 36 up against ashoulder 32c on shaft 32.

Housings 26 and 28 are rigidly secured together by a plurality of bolts68 which pass through smooth bores 70 in housing 28 for threaded receiptin tapped bores 72 in housing 26. Thus secured together, and withparticular reference now to FIGS. 4-7, housings 26 and 28 coact todefine an annular chamber 74 slideably receiving, in piston fashion, anannular nozzle assembly 76 and a throttling ring 78.

Nozzle assembly 76 includes a support ring 79, a support ring 80, afirst nozzle blade set comprising a plurality of blades 82circumferentially spaced about the central turbomotor axis and eachdisposed at a first angle (FIG. 7) with respect to the orbit of radialwheel 48, and a second nozzle blade set comprising a plurality of blades84 circumferentially spaced about the central turbomotor axis and eachdisposed at a second angle with respect to the radial wheel orbit. Theblades 82 of the first blade set are each integral at one end withsupport ring 79 and project axially therefrom in cantilever fashion topresent a free edge 82a; and the blades 84 of the second blade setextend in bridge fashion between support rings 79 and 80.

Throttling ring 78 is in the form of an annular block and presents anannular face 78a in confronting relation to the free blade edges 82a;ring 78 has a plurality of axially extending pockets 86 formed thereineach of a shape to snugly receive a blade 82 and each opening in annularface 78a.

Sealing rings or gaskets 87 carried by support ring serve to define asealed annular subchamber 88 to the right (FIG. 4) of support ring 80,and pressurized control fluid may be supplied to subchamber 88 through abore 90 provided in one or more bolts 68 communicating with a cross bore92 opening at its radially inner end in chamber 88 and plugged at itsradially outer end by a plug 94. Stop means 96 constituted by one ormore bosses formed integral with housing 26 coacts with support ring 80to define the extreme rightward position (FIG. 4) of nozzle assembly 76.

Sealing rings or gaskets 98 carried by throttling ring 78 serve todefine a sealed annular subchamber 100 to the left of ring 78, andpressurized control fluid may be supplied to chamber 100 through a bore102 in the adjacent wall portion of housing 28. Stop means 104 constituted by one or more bosses integral with housing 28 coacts with theleft face of throttling ring 78 to define the extreme leftward positionof the throttling ring.

Working fluid is delivered to nozzle assembly 76 through an annularopening 106 defined between axially spaced annular walls 26b and 280.Space 106 is defined and maintained by interfitting bosses 26c and 28dformed integral with housings 26 and 28 and passing bolts 68. Workingfluid is in turn delivered to space 106 through a scroll 108 encirclingspace 106 and secured to housings 26, 28 by a pair of annuluses 109, l10 fitted over the radially outer periphery of housings 26, 28respectively.

The invention turbomotor includes a brake assembly seen generally at 112in FIG. 3. Brake assembly 112 includes an enlarged drum 114 havingtrunnions 1 16 and l 18, joumalling the drum in a central chamber 113defined within hub portion 30a of brake housing 30. Trunnion 116 isjournalled in a ball bearing 120 received in a sleeve 122 positioned inan end cap 124 secured by screws 126 to the left end of the hub portion30a. Bearing 120 is maintained in a snug, preloaded condition by springmeans 127. Trunnion 118 is journalled in a ball bearing 128 received inhub portion 30a and includes a splined extention 119 which is coupled tothe splined left end of turbomotor shaft 32 by a splined sleeve coupling121. Nut 123 on a threaded portion of trunnion 118 maintains bearing 128in a snug condition.

A sleeve 130 of phenolic-asbestos material (e.g., Pyrotex made byRaybestos-Manhattan Inc. of Passaic, New-Jersey) loosely surrounds drum114 and is adapted to be contracted to brakingly grasp the drum byhydraulic pressure introduced into the sealed annular chamber 132between the exterior surface of the sleeve and the surface of housingchamber 113. Hydraulic fluid is introduced into chamber 132 through abore 134 extending through a spoke 136 of brake housing 30 forconnection to a suitable hose fitting 138. The exterior surface ofsleeve 130 has grounding splines 130a which coact with mating splines113a on the cylindrical wall surface of chamber 113 to ground the sleevethrough the brake housing in both the relaxed and the contractedcondition of sleeve 130. Further details of the construction andoperation of contracting sleeve 130 may be found in U.S. Pat.application Ser. No. 763,784 filed on Sept. 30, 1968 and assigned to theassignee of the present invention. The entire brake assembly is amodular unit and may be disconnected from the turbomotor by removal of aclamp ring 140 coupling housing units 28 and 30.

The output shaft 32 of the turbomotor drives hoist drum through asuitable gear reducer seen generally at 144. Gear reducer 144 is securedto the journal portion 17 of carriage 16 by a plurality of bolts 146(see also FIG. 2) passing through an inturned flange 17a of carriagejournal portion 17 and through gear reducer 144 for coaction with nuts148 and turbomotor 22 is in turn secured to gear reducer 144 by theextended portion 68a of those screw bolts 68 that are not hollowed outfor transmission of pressure fluid to subchamber 88. Turbomotor 22 isthus, in effect, carried by carriage 16. Gear reducer 144, for example,may comprise a Breeze Cyclocentric Drive available in various reductionratios from Breeze Corporation Inc., Union, New Jersey. CyclocentricDrives are available either with or without a rotational directionchange between the input shaft and the output ring gear (150); thepresent disclosure contemplates a Cyclocentric Drive in which the outputring gear 150 rotates in a reverse direction from input shaft 32. Outputring gear 150 is drivingly coupled to drum 10 by a plurality of screwbolts 152 passing through an internal flange 10a on drum 10 for threadedengagement with suitable tapped bores in output ring gear 150. Drum 10is thus driven through gear reducer 144 at a rotational speed which isreduced with respect to that of turbomotor output shaft 32 by a degreedetermined by the reduction ratio provided by reducer 144.

OPERATION OF PREFERRED EMBODIMENT The operation of the inventionturbomotor will now be described with reference to its use in thedisclosed hoist apparatus. When the hoist drum is not being rotated topay-in or pay-out the cable, braking sleeve 130 is maintained in acontracted condition by hydraulic fluid introduced into chamber 132through fitting 138. Sleeve 130 thus acts as a static brake for thehoist. When it is desired to rotate drum l0, hydraulic pressure isrelieved in chamber 132 to release the static brake and pressurizedworking fluid (e.g. air) is supplied to scroll 108 through a suitablehose 160 (FIG. I); scroll 108 distributes the working fluid around theperiphery of the motor and the fluid passes selectively through annularspace 106 into chamber 74 where it coacts with nozzle assembly 76. Inthe absence of pressurized control fluid (e.g. air) in chambers 88 and100, nozzle assembly 76 and throttling ring 78 assume their splayedapart positions of FIG. 4 in which each is pushed up against itsrespective stop means by the pressure of the working fluid. Blades 82are thus the working blades at this time and determine the angle atwhich the working fluid will be delivered to radial turbine wheel 48. Inthe disclosed hoist embodiment, blades 82 are placed at an angle suchthat it causes the drum to be rotated in a paying-in direction(clockwise in FIG. 2) to lift a load on hook 13. The angle of blades 82is best seen in FIG. 7; it will be seen that blades 82 function todirect working fluid against the radial inflow portions 540 of radialturbine wheel blades 54 at an angle to cause wheel 48 to rotate incounterclockwise direction as viewed in FIG. 7.

When it is desired to pay-out the cable, i.e., reverse the direction ofrotation of drum 10, turbomotor 22 is reversed by directing pressurizedcontrol fluid into chamber 88 throughbores and 92 to move nozzleassembly 76 to the left to the position shown in FIG. 6 in which blades84 are now in working position with respect to the radial turbine wheelblades. Blades 84, as best seen in FIG. 7, are angled in an oppositesense to blades 82 and function to direct the working fluid againstturbine blades 54 in a sense to produce clockwise rotation of turbinewheel 48 as viewed in FIG. 7. The leftward movement of nozzle assembly76 in chamber 74 is made possible by the receipt of blades 82 in pockets86 in blocking ring 78. When it is desired to pay-in the cable again,control pressure in chamber 88 is relieved and control pressure isestablished in chamber blocking ring 78 is thus moved rightward inchamber 74 to push nozzle assembly 76 back to its FIG. 5 position upagainst stop 96. When nozzle assembly 76 has been pushed to its stopposition, control pressure is relieved in chamber 100 and the pressureof the working fluid passing through the nozzle structure acts to pushblocking ring leftward to its stop position so that parts 76, 78 againassume the positions of FIG. 4.

If it is desired, while operating in the paying-in position of FIG. 4,to modulate the nozzle structure to vary the flow of working fluid tothe radial turbine, a control fluid pressure is established in chamber100 of a magnitude to overcome the pressure of the working fluid andslide throttling ring 78 rightward in chamber 74; as ring 78 movesrightward, blades 82 are selectively and progressively received orswallowed up in pockets 86 so that the effective working area of blades82 is selectively and progressively reduced. In the FIG. 5configuration, for example, the working area of blades 82 has beenreduced to a fraction of their working area in FIG. 4 by the rightwardswallowing movement of blocking ring 78. Blocking ring 78 may beselectively positioned anywhere along the width of blades 82 to providean infinite number of modulated positions with such selectivepositioning being accomplished by selective control of the pressure inchamber 100 relative to the pressure of the working fluid passingthrough the nozzle structure. 7

Whether operating in the paying-in mode of FIG. 4 or the paying-out modeof FIG. 6, the working fluid directed by the nozzle blades into radialturbine wheel 48 flows through radial inflow portions 54a and thencethrough the axial outflow passages defined between adjacent axialdischarge blade portions 54b for discharge at the left axial face (FIG.3) of the radial turbine wheel into axial turbine wheel nozzle structure56. The blades 56b of nozzle structure 56 in turn directs the workingfluid against the blades 60b of axial turbine wheel 60 and the workingfluid leaving turbine wheel 60 flows around the hub 44 a of wheel 44 andaround. the hub 30a of housing 30 for discharge through annular opening162.

According to an important feature of the invention, the blades of theaxial turbine wheel and the axial turbine wheel nozzle are relativelypositioned such that the axial turbine windmills at the design point ofthe turbomotor. Specifically, and with particular reference to FIG. 11,the blades 60b of the axial turbine are positioned at an angle suchthat, at the rated speed of the turbomotor, the vectorial sum V, of therelative fluid leaving velocity V of the axial turbine blades and theblade tangential velocity V of the axial turbine blades is substantiallyequal to the vector V of the fluid leaving nozzle blades 56b. Thus, atrated or design speed of the turbometer, the working fluid in passingthrough the axial turbine wheel undergoes no change in direction and,disregarding friction losses, undergoes no change in pressure so thatthe working fluid gives up substantially no work to the axial turbineand the axial turbine simply windmills, contributing no torque to thetorque output of the turbomotor. In the disclosed embodiment, whereinthe turbomotor has a design speed of approximately 35,000 RPM, the axialturbine blades 60b are arranged such that the relative fluid leavingvelocity V has a direction substantially parallel to the axis of theturbomotor and the axial turbine nozzle blades are arranged such thatthe nozzle blade tangential velocity V N has a direction at asignificant angle with respect to the turbomotor axis; however, when theturbine blade tangential velocity V for the turbomotor running at itsdesign speed of e.g. 35,000 RPM is vectorially summed with the leavingvelocity V the resultant velocity vector V corresponds in both magnitudeand direction to the vector V These relationships are also illustratedin the stall torque ratio graph of FIG. 12. Stall torque ratio isdefined as the ratio of the torque at which the turbomotor will stall tothe design torque of the turbomotor. FIG. 12 has percentage of designtorque as the ordinate and percentage of design speed as the abscissa.From the graph, it will be seen that the axial turbine contributesmaximum torque at zero speed and ceases to contribute any torque at onehundred percent of design speed (i.e., at design speed). The radialturbine also contributes maximum torque at zero speed but is stillcontributing substantial torque at design speed, at which point it iscontributing all of the turbomotor torque since the axial wheel is nowwindmilling. The described axialradial combination produces a turbomotorhaving a higher stall torque ratio than either the radial turbine aloneor the axial turbine alone, and yet has the ability to operate withmoderate efficiency in reverse. If the axial turbine were arranged toproduce significant torque at design speed, it would seriously hamper oreven eliminate operation of the turbomotor in reverse. Thus, asrepresented on the graph by the dash line curve labelled ATl, if theaxial turbine were designed to have a higher torque curve than theinvention curve, e.g. a torque curve representing sixty percent of thetorque curve for the radial unit, the axial turbine would contribute toturbomotor torque at design speed but would eliminate the reverseoperational mode since, assuming sixty percent efficiency for the radialwheel in reverse, the radial wheel reverse torque would be cancelled atall speeds by the drag of the axial turbine. Similarly, as representedon the graph by the dash line curve labelled ATZ, if the axial turbinewere designed to have a lower torque curve than the invention curve, theaxial turbine would have less of a drag effect in the reverse mode butwould also generate a considerable drag at design speed in the forwardmode. The described arrangement, wherein the axial stage is designed towindmill at design speed, is thus seen to present a happy marriage ofthe radial and axial turbine characteristics and is seen to be an idealturbomotor for use in applications, such as the disclosed hoistapplication, where good torque is required in the forward" (pay-in) modebut yet an operational and usable reverse (pay-out) mode is alsorequired.

MODIFIED NOZZLE CONSTRUCTION A modification of the FIG. 4-7 radialturbine wheel nozzle construction is shown in FIGS. 13 and 14 in whichparts which are in common with or similar to the FIG. 4-7 constructionare given corresponding reference numerals but with a prime added. Inthe FIG. I3 and 14 modification, the blocking ring 78 is replaced with astructure whereby the blades 82' may be selectively pivoted about axesgenerally parallel to the turbomotor axis. The nozzle assembly 76' ofFIGS. 13 and 14, in addition to support rings 79' and 80' and bridgingblades 84, includes a plurality of strut members 168 integral withsupport ring 79' and extending therefrom in cantilever fashion tooverlie each blade 82', a first ring member 170 secured to assembly 76'by screw bolts 172 received in threaded bores in strut members 168, anda second ring member 174 secured to first ring member 170 by screw bolts176. An externally toothed ring gear 178 is joumalled in an annularcavity 180 in ring member 174 by a ball race 182. Ring gear 178 engagesa plurality of splined shafts 184; each shaft 184 terminates at one endin a pin portion 186 journalled in support ring 79. Each blade 82' iskeyed to a respective pin portion 186 so that the blade is rotated byrotation of the corresponding shaft 184. The illustrated shaft 184extends leftwardly for splined receipt in an internally splined sleeve188 positioned in the adjacent wall portion of housing 26; the remainingshafts 184 are stub shafts which are joumalled at their left ends in theleft or inner wall portion 190 of ring member 174 with their splinesengaged with the teeth of ring gear 178. A handle 192 is secured to theleft end of sleeve 188. When handle 192 is turned, the illustrated blade82' is rotated directly; ring gear 178 is also rotated by rotation ofthe illustrated shaft 184 and ring gear 178 in turn rotates stub shafts184 so that all blades 82' are rotated in unison. Nozzle assembly 76 isshown in the forward or pay-in mode in FIG. 13 in which incoming workingfluid is directed into radial wheel 48 by blades 82'. The angle andeffective working area of blades 82' (see FIG. 14) may be selectivelymodulated byselective rotation of handle 192. Reversal of nozzleassembly 76' is accomplished as in the embodiment of FIG. 4-7 byadmission of pressurized control fluid into annular subchamber 88through bolt passage 90' and cross bore 92. Leftward movement of thenozzle assembly to bring blades 84' into working position is allowed andguided by sliding movement of the illustrated spline shaft 184 in thesplined bore of sleeve 188. With blades 84' in working position, theworking fluid is directed into radial wheel 48' at an angle (see FIG.14) to cause rotation of wheel 48' in a reverse or pay-out direction.Nozzle 76' may be returned to the forward mode position of FIG. 13 byrelease of control pressure in subchamber 88 and admission ofpressurized control fluid into subchamber 100 through a suitable port(not shown) in housing 26.

While the invention has been illustrated and described in detail withreference to the disclosed embodiments, it will be understood thatvarious changes and modifications may be made in the disclosedembodiments without departing from the scope or spirit of the invention.

I claim:

1. A fluid turbomotor comprising:

A. means defining a housing;

B. a radial turbine wheel of the radial inflow type;

C. means mounting said turbine wheel for rotation within said housingabout its central axis;

D. a nozzle ring structure positioned in said housing concentric withsaid axis and encircling said turbine wheel, said nozzle ring structureincluding 1. a support ring,

2. a first blade set comprising a plurality of blades circumferentiallyspaced about said axis and disposed at a first angle with respect to theorbit of said wheel, the blades of said first blade set are integral atone end with said support ring and project therefrom in cantileverfashion to present a free edge, and

3. a second blade set spaced axially from said first blade set andcomprising a plurality of blades circumferentially spaced about saidaxis and disposed at a second angle with respect to said orbit;

E. means mounting said ring structure in said housing for axial movementrelative to said wheel between 1. a first position axially aligning saidfirst blade set with the outer periphery of said wheel and axiallydisplacing said second blade set with respect to said outer periphery,whereby working fluid may be directed through said first blade setagainst the vanes of said turbine wheel at said first angle, and

2. a second position axially aligning said second blade set with saidouter periphery and axially displacing said first blade set with respectto said outer periphery, whereby fluid may be directed through saidsecond blade set against the vanes of said turbine wheel at said secondangle;

F. a ring member disposed within said housing in side-by-side relationto said first blade set and presenting an annular face in confrontingrelation to said free edges, said ring member having a plurality ofaxially extending pockets formed therein each of a shape to snuglyreceive a respective blade of said first blade set and each opening insaid confronting annular face; and

G. means mounting said ring member for axial movement within saidhousing relative to said nozzle ring structure to selectively receivethe blades of said first blade set within said pockets and therebyselectively vary the effective, exposed working area of the blades ofsaid first blade set.

2. A fluid turbomotor according to claim 1 wherein H. said mountingmeans comprises means defining an annular chamber within said housingconcentric with said axis and encircling said radial turbine wheel;

I. said nozzle ring structure comprises an annular first pistonslideably received in said chamber for axial reciprocation toselectively move said nozzle ring structure between said first andsecond positions; and

J. said ring member comprises an annular second piston slideablyreceived in said chamber in tandem relation to said first piston andarranged for axial reciprocation relative to said first piston toselectively vary the effective working area of said first set blades.

3. A fluid turbomotor according to claim 2 and further including K.first sealing means defining a first sealed subcham ber within saidchamber between an annular end wall of said chamber and the adjacentannular end wall of said first piston;

L. first conduit means opening in said first subchamber for introducingpressurized control fluid into said first subchamber to reciprocate saidfirst piston in said chamber between said first and second positions;

M. second sealing means defining a second sealed subchamber within saidchamber between the other annular end of said chamber and the adjacentannular end wall of said second piston; and

N. second conduit means opening in said second subchamber forintroducing pressurized control fluid into said second subchamber toreciprocate said second piston in said chamber relative to said firstpiston to selectively vary the effective working area of said first setblades.

4. A fluid turbomotor comprising A. means defining a housing;

B. a radial turbine wheel of the radial inflow type;

C. means mounting said turbine wheel for rotation within said housingabout its central axis;

D. a nozzle ring structure positioned in said housing concentric withsaid axis and encircling said turbine wheel, said nozzle ring structureincluding 1. a support ring portion, and 2. a plurality of bladescircumferentially spaced about said axis and integral at one end withsaid support ring and projecting axially therefrom in centilever fashionto present a free edge;

E. a ring member disposed within said housing in side-by-side relationto said blades and presenting an annular face in confronting relation tosaid free blade edges,

said ring member having a plurality of axially extending pockets formedtherein each of a shape to snugly receive a respective blade and eachopening in said confronting annular face; and

F means mounting said ring member for axial movement within said housingrelative to said nozzle ring structure to selectively receive saidblades within said pockets and thereby selectively vary the effective,exposed working area of said blades.

5. A fluid turbomotor according to claim 4 wherein G. said mountingmeans comprises means defining an annular chamber within said housingconcentric with said axis and encircling said radial turbine wheel; and

H. said ring member comprises an annular piston slideably received insaid chamber for axial reciprocation in said chamber to selectively varythe effective working area of said first set blades.

6. A fluid turbomotor comprising:

A. means defining a housing;

B. a radial turbine wheel of the radial inflow type;

C. means mounting said turbine wheel for rotation within said housingabout its central axis;

D. a nozzle ring structure positioned in said housing concentric withsaid axis and encircling said turbine wheel, said nozzle ring structureincluding 1. a first blade set comprisng a plurality of bladescircumferentially spaced about said axis and each disposed at an anglevariable with respect to the orbit of said wheel,

2. means mounting the blades of said first blade set for pivotalmovement relative to said ring structure about axes parallel to saidaxis,

3. means for pivoting the blades of said first blade set in unison aboutsaid axes, and

4. a second blade set spaced axially from said first set and comprisinga plurality of blades circumferentiaily spaced about said axis and eachdisposed at a fixed angle with respect to said orbit; E. means mountingsaid ring structure in said housing for axial movement relative to saidwheel between 1. a first position axially aligning said first blade setwith the outer periphery of said wheel and axially displacing saidsecond with respect to said outer periphery, whereby working fluid maybe directed through said first blade set against the vanes of saidturbine wheel at said variable angle, and 2. a second position axiallyaligning said second blade set with said outer periphery of said wheeland axially displacing said first biade set with respect to said outerperiphery, whereby fluid may be directed through said second blade setagainst the vanes of said turbine wheel at said fixed angle.

1. A fluid turbomotor comprising: A. means defining a housing; B. aradial turbine wheel of the radial inflow type; C. means mounting saidturbine wheel for rotation within said housing about its central axis;D. a nozzle ring structure positioned in said housing concentric withsaid axis and encircling said turbine wheel, said nozzle ring structureincluding
 1. a support ring,
 2. a first blade set comprising a pluralityof blades circumferentially spaced about said axis and disposed at afirst angle with respect to the orbit of said wheel, the blades of saidfirst blade set are integral at one end with said support ring andproject therefrom in cantilever fashion to present a free edge, and
 3. asecond blade set spaced axially from said first blade set and comprisinga plurality of blades circumferentially spaced about said axis anddisposed at a second angle with respect to said orbit; E. means mountingsaid ring structure in said housing for axial movement relative to saidwheel between
 1. a first position axially aligning said first blade setwith the outer periphery of said wheel and axially displacing saidsecond blade set with respect to said outer periphery, whereby workingfluid may be directed through said first blade set against the vanes ofsaid turbine wheel at said first angle, and
 2. a second position axiallyaligning said second blade set with said outer periphery and axiallydisplacing said first blade set with respect to said outer periphery,whereby fluid may be directed through said second blade set against thevanes of said turbine wheel at said second angle; F. a ring memberdisposed within Said housing in side-by-side relation to said firstblade set and presenting an annular face in confronting relation to saidfree edges, said ring member having a plurality of axially extendingpockets formed therein each of a shape to snugly receive a respectiveblade of said first blade set and each opening in said confrontingannular face; and G. means mounting said ring member for axial movementwithin said housing relative to said nozzle ring structure toselectively receive the blades of said first blade set within saidpockets and thereby selectively vary the effective, exposed working areaof the blades of said first blade set.
 2. a first blade set comprising aplurality of blades circumferentially spaced about said axis anddisposed at a first angle with respect to the orbit of said wheel, theblades of said first blade set are integral at one end with said supportring and project therefrom in cantilever fashion to present a free edge,and
 2. A fluid turbomotor according to claim 1 wherein H. said mountingmeans comprises means defining an annular chamber within said housingconcentric with said axis and encircling said radial turbine wheel; I.said nozzle ring structure comprises an annular first piston slideablyreceived in said chamber for axial reciprocation to selectively movesaid nozzle ring structure between said first and second positions; andJ. said ring member comprises an annular second piston slideablyreceived in said chamber in tandem relation to said first piston andarranged for axial reciprocation relative to said first piston toselectively vary the effective working area of said first set blades. 2.a second position axially aligning said second blade set with said outerperiphery and axially displacing said first blade set with respect tosaid outer periphery, whereby fluid may be directed through said secondblade set against the vanes of said turbine wheel at said second angle;F. a ring member disposed within Said housing in side-by-side relationto said first blade set and presenting an annular face in confrontingrelation to said free edges, said ring member having a plurality ofaxially extending pockets formed therein each of a shape to snuglyreceive a respective blade of said first blade set and each opening insaid confronting annular face; and G. means mounting said ring memberfor axial movement within said housing relative to said nozzle ringstructure to selectively receive the blades of said first blade setwithin said pockets and thereby selectively vary the effective, exposedworking area of the blades of said first blade set.
 2. means mountingthe blades of said first blade set for pivotal movement relative to saidring structure about axes parallel to said axis,
 2. a second positionaxially aligning said second blade set with said outer periphery of saidwheel and axially displacing said first blade set with respect to saidouter periphery, whereby fluid may be directed through said second bladeset against the vanes of said turbine wheel at said fixed angle.
 2. aplurality of blades circumferentially spaced about said axis andintegral at one end with said support ring and projecting axiallytherefrom in centilever fashion to present a free edge; E. a ring memberdisposed within said housing in side-by-side relation to said blades andpresenting an annular face in confronting relation to said free bladeedges, said ring member having a plurality of axially extending pocketsformed therein each of a shape to snugly receive a respective blade andeach opening in said confronting annular face; and F. means mountingsaid ring member for axial movement within said housing relative to saidnozzle ring structure to selectively receive said blades within saidpockets and thereby selectively vary the effective, exposed working areaof said blades.
 3. A fluid turbomotor according to claim 2 and furtherincluding K. first sealing means defining a first sealed subchamberwithin said chamber between an annular end wall of said chamber and theadjacent annular end wall of said first piston; L. first conduit meansopening in said first subchamber for introducing pressurized controlfluid into said first subchamber to reciprocate said first piston insaid chamber between said first and second positions; M. second sealingmeans defining a second sealed subchamber within said chamber betweenthe other annular end of said chamber and the adjacent annular end wallof said second piston; and N. second conduit means opening in saidsecond subchamber for introducing pressurized control fluid into saidsecond subchamber to reciprocate said second piston in said chamberrelative to said first piston to selectively vary the effective workingarea of said first set blades.
 3. means for pivoting the blades of saidfirst blade set in unison about said axes, and
 3. a second blade setspaced axially from said first blade set and comprising a plurality ofblades circumferentially spaced about said axis and disposed at a secondangle with respect to said orbit; E. means mounting said ring structurein said housing for axial movement relative to said wheel between
 4. asecond blade set spaced axially from said first set and comprising aplurality of blades circumferentially spaced about said axis and eachdisposed at a fixed angle with respect to said orbit; E. means mountingsaid ring structure in said housing for axial movement relative to saidwheel between
 4. A fluid turbomotor comprising A. means defining ahousing; B. a radial turbine wheel of the radial inflow type; C. meansmounting said turbine wheel for rotation within said housing about itscentral axis; D. a nozzle ring structure positioned in said housingconcentric with said axis and encircling said turbine wheel, said nozzlering structure including
 5. A fluid turbomotor according to claim 4wherein G. said mounting means comprises means defining an annularchamber within said housing concentric with said axis and encirclingsaid radial turbine wheel; and H. said ring member comprises an annularpiston slideably received in said chamber for axial reciprocation insaid chamber to selectively vary the effective working area of saidfirst set blades.
 6. A fluid turbomotor comprising: A. means deFining ahousing; B. a radial turbine wheel of the radial inflow type; C. meansmounting said turbine wheel for rotation within said housing about itscentral axis; D. a nozzle ring structure positioned in said housingconcentric with said axis and encircling said turbine wheel, said nozzlering structure including